U.S. patent number 11,260,989 [Application Number 16/659,739] was granted by the patent office on 2022-03-01 for aircraft beacon light, aircraft wing, aircraft beacon light system, and method of supplementing an aircraft beacon light system.
This patent grant is currently assigned to GOODRICH LIGHTING SYSTEMS GMBH. The grantee listed for this patent is Goodrich Lighting Systems GmbH. Invention is credited to Marion Depta, Andre Hessling-Von Heimendahl, Anil Kumar Jha, Norbert Menne.
United States Patent |
11,260,989 |
Jha , et al. |
March 1, 2022 |
Aircraft beacon light, aircraft wing, aircraft beacon light system,
and method of supplementing an aircraft beacon light system
Abstract
An aircraft beacon light for an aircraft wing with a foldable
wing tip includes a housing, a lens cover, and at least one light
source arranged between the housing and the lens cover, wherein the
aircraft beacon light is configured to emit flashes of red light in
operation, and wherein the housing and the lens cover are shaped to
embed the aircraft beacon light into a hinge assembly coupling the
foldable wing tip to a main wing portion of the aircraft wing.
Inventors: |
Jha; Anil Kumar (Lippstadt,
DE), Hessling-Von Heimendahl; Andre (Koblenz,
DE), Depta; Marion (Lippstadt, DE), Menne;
Norbert (Paderborn, DE) |
Applicant: |
Name |
City |
State |
Country |
Type |
Goodrich Lighting Systems GmbH |
Lippstadt |
N/A |
DE |
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|
Assignee: |
GOODRICH LIGHTING SYSTEMS GMBH
(Lippstadt, DE)
|
Family
ID: |
1000006145362 |
Appl.
No.: |
16/659,739 |
Filed: |
October 22, 2019 |
Prior Publication Data
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Document
Identifier |
Publication Date |
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US 20200122857 A1 |
Apr 23, 2020 |
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Foreign Application Priority Data
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Oct 22, 2018 [EP] |
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18201803.6 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64D
47/06 (20130101); F21S 43/14 (20180101); F21S
43/20 (20180101); F21W 2107/30 (20180101); F21Y
2115/10 (20160801); B64D 2203/00 (20130101); F21W
2103/15 (20180101) |
Current International
Class: |
B64D
47/06 (20060101); F21S 43/20 (20180101); F21S
43/14 (20180101) |
References Cited
[Referenced By]
U.S. Patent Documents
Foreign Patent Documents
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2676878 |
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Dec 2013 |
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EP |
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2857309 |
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Apr 2015 |
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EP |
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3284684 |
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Feb 2018 |
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EP |
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3626630 |
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Mar 2020 |
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EP |
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Other References
Extended European Search Report for International Application No.
18201803.6 dated Mar. 4, 2019, 8 pages. cited by applicant .
EP Office Action for Application No. 18201803.6, dated Mar. 5,
2021, 5 pages. cited by applicant.
|
Primary Examiner: Bolourchi; Nader
Attorney, Agent or Firm: Cantor Colburn LLP
Claims
The invention claimed is:
1. Aircraft beacon light for an aircraft wing with a foldable wing
tip, the aircraft beacon light comprising: a housing, a lens cover,
and at least one light source arranged between the housing and the
lens cover, wherein the aircraft beacon light is configured to emit
flashes of red light in operation, and wherein the housing and the
lens cover are shaped to embed the aircraft beacon light into a
hinge assembly coupling the foldable wing tip to a main wing
portion of the aircraft wing; wherein the housing and the lens
cover are shaped to embed the aircraft beacon light into a lateral
end of the main wing portion of the aircraft wing, wherein the lens
cover has a substantially flat first lens cover portion configured
to form part of a side face of the main wing portion of the
aircraft wing, when the foldable wing tip is in a folded up
position, and wherein the lens cover further comprises a second
lens cover portion configured to form part of an underside of the
main wing portion, when the aircraft beacon light is connected to
the lateral end of the main wing portion, with the second lens
cover portion forming part of the underside of the main wing
portion both when the foldable wing tip is in the folded up
position and when the foldable wing tip is in a laterally extended
position.
2. Aircraft beacon light according to claim 1, wherein the at least
one light source is at least one red light source, in particular at
least one red LED.
3. Aircraft beacon light according to claim 1, wherein the lens
cover is or comprises a red light filter.
4. Aircraft wing, comprising: a main wing portion, a foldable wing
tip, a hinge assembly coupling the main wing portion and the
foldable wing tip, and an aircraft beacon light according to any of
the preceding claims, embedded into the hinge assembly such that
the substantially flat first lens cover portion forms part of the
side face of the main wing portion when the foldable wing tip is in
the folded up position, and that the second lens cover portion
forms part of the underside of the main wing portion, both when the
foldable wing tip is in the folded up position and when the
foldable wing tip is in the laterally extended position.
5. Aircraft wing according to claim 4, wherein the hinge assembly
is configured to allow for a motion of the foldable wing tip
between a laterally extended position and a folded up position and
wherein the foldable wing tip exposes at least part of the lens
cover of the aircraft beacon light, when in the folded up
position.
6. Aircraft wing according to claim 4, wherein the hinge assembly
comprises a plurality of first teeth, which are an integral part of
the main wing portion, and a plurality of second teeth, which are
an integral part of the foldable wing tip, and wherein the aircraft
beacon light is arranged in one of the plurality of first teeth;
wherein the plurality of first teeth and the plurality of second
teeth are engaged with each other via a rotation axis of the
foldable wing tip.
7. Aircraft wing according to any of claim 4, wherein the aircraft
beacon light is configured to emit the flashes of red light over a
horizontal opening angle of between 5.degree. and 30.degree., in
particular over a horizontal opening angle of between 5.degree. and
20.degree., further in particular over a horizontal opening angle
of between 5.degree. and 15.degree..
8. Aircraft wing according any of claim 7, wherein the aircraft
beacon light is configured to emit the flashes of red light over a
vertical opening angle of between 5.degree. and 180.degree., in
particular over a vertical opening angle of between 5.degree. and
150.degree., further in particular over a vertical opening angle of
between 5.degree. and 30.degree..
9. Aircraft wing according to any of claim 8, wherein the aircraft
beacon light is configured to emit the flashes of red light over a
solid angle containing a projection of the foldable wing tip, when
in the folded up position, as projected from the position of an
upper fuselage-mounted beacon light.
10. The aircraft wing according to claim 4, wherein the aircraft
beacon light is configured to emit the flashes of red light over a
vertical opening angle of between 5.degree. and 180.degree..
11. The aircraft wing according to claim 4, wherein the aircraft
beacon light is configured to emit the flashes of red light over a
vertical opening angle of between 5.degree. and 150.degree..
12. The aircraft wing according to claim 4, wherein the aircraft
beacon light is configured to emit the flashes of red light over a
vertical opening angle of between, further in particular over a
vertical opening angle of between 5.degree. and 30.degree..
13. The aircraft wing according to claim 4, wherein the aircraft
beacon light is configured to emit the flashes of red light over a
solid angle containing a projection of the foldable wing tip, when
in the folded up position, as projected from the position of an
upper fuselage-mounted beacon light.
14. An aircraft beacon light system, comprising: an upper
fuselage-mounted beacon light configured to emit flashes of red
light in operation, a lower fuselage-mounted beacon light
configured to emit flashes of red light in operation, a right wing
aircraft beacon light that is an aircraft beacon light according to
claim 1, and a left wing aircraft beacon light that is an aircraft
beacon light according to claim 1.
15. The aircraft beacon light system according to claim 14, wherein
the upper fuselage-mounted beacon light, the lower fuselage-mounted
beacon light, the right wing aircraft beacon light and the left
wing aircraft beacon light are synchronized with respect to
emitting the flashes of red light.
16. A method of supplementing an aircraft beacon light system
having an upper fuselage-mounted beacon light and a lower
fuselage-mounted beacon light, the method comprising: emitting
flashes of red light from a hinge assembly of the aircraft wing
according to claim 6 through the substantially flat first lens
cover portion of the lens cover, when the foldable wing tip of the
aircraft wing is in the folded up position; and emitting flashes of
red light through the second lens cover portion of the lens cover
both when the foldable wing tip is in the folded up position and
when the foldable wing tip is in the laterally extended
position.
17. The method according to claim 16, wherein said emitting the
flashes of red light comprises emitting flashes of red light over a
solid angle containing a projection of the foldable wing tip, when
in the folded up position, as projected from the position of the
upper fuselage-mounted beacon light.
Description
FOREIGN PRIORITY
This application claims priority to European Patent Application No.
18201803.6 filed Oct. 22, 2018, the entire contents of which is
incorporated herein by reference.
TECHNICAL FIELD
The present invention relates to exterior aircraft lighting. In
particular, it relates to aircraft beacon light systems, i.e. to
aircraft light systems that emit flashes of red light in order to
indicate that the engines of the aircraft are running.
BACKGROUND
Almost all aircraft are equipped with exterior lighting systems.
For example, large commercial aircraft have many different exterior
lights. An exemplary group of exterior aircraft lights are lights
for passive visibility, such as navigation lights, white strobe
anti-collision lights, red flashing beacon lights and logo lights.
Another exemplary group of exterior aircraft lights are headlights
that allow the pilots to view the area in front of them, when they
are seated in the cockpit, such as taxi lights, takeoff lights,
landing lights, and runway turn-off lights. Yet another example of
exterior aircraft lights are scan lights that allow the inspection
of the aircraft structure in the dark, such as wing scan lights and
engine scan lights.
Modern air planes are made in various different models. Existing
exterior aircraft lights do not fit all of these models in all
operating regimes in an entirely satisfactory manner. Accordingly,
it would be beneficial to provide an exterior aircraft light that
addresses shortcomings in the light output of particular kinds of
aircraft.
SUMMARY
Exemplary embodiments of the invention include an aircraft beacon
light for an aircraft wing with a foldable wing tip, the aircraft
beacon light comprising a housing; a lens cover; and at least one
light source arranged between the housing and the lens cover;
wherein the aircraft beacon light is configured to emit flashes of
red light in operation; and wherein the housing and the lens cover
are shaped to embed the aircraft beacon light into a hinge assembly
coupling the foldable wing tip to a main wing portion of the
aircraft wing.
Exemplary embodiments of the invention allow for enhancing the
beacon light output of aircraft that have wing structures with
foldable wing tips. In particular, an aircraft beacon light that is
shaped to be embedded into the hinge assembly between the foldable
wing tip and the main wing portion may complete the beacon light
output of the aircraft, when the folded up foldable wing tip
shadows part of the beacon light output of other beacon lights.
Further in particular, the foldable wing tip, when in the folded-up
position, may block some of the light emitted by an aircraft beacon
light arranged on an upper portion of the aircraft fuselage. The
resulting gap in the beacon light output may be filled by the
aircraft beacon light in accordance with exemplary embodiments of
the invention. By embedding an aircraft beacon light into the hinge
assembly, coupling the foldable wing tip and the main wing portion
of an aircraft wing, the enhancing beacon light output may be
conveniently provided when the foldable wing tip is in a folded-up
position. The aircraft beacon light may be fully integrated into
the aircraft wing, when the foldable wing tip is in a laterally
extended position. In this way, the aircraft beacon light may not
have any effect on the aerodynamics of the aircraft wing. The
folding up of the foldable wing tip may expose the additional
aircraft beacon light and may allow for the emission of the desired
light output for filing the gaps in the beacon light output of the
aircraft. Accordingly, an effective enhancing of the beacon light
output may be achieved, when the foldable wing tip is in the folded
up position, without any detrimental effect on the aerodynamics of
the aircraft wing, when the foldable wing tip is in the laterally
extended position.
Exemplary embodiments of the invention allow for the provision of
an aircraft beacon light that contributes to facilitating a
comprehensive beacon light output, both when the foldable wing tip
of the aircraft is in a folded up position and when the foldable
wing tip is in a laterally extended position. In this way, it may
be possible to fold up the wing tips of an aircraft model having
foldable wing tips during taxiing on an airport, without
compromising the signalling safety provided by the beacon light
system. In addition to folding up the wing tips in an aircraft's
parking position, which may be done for saving space on airports,
the wing tips of an aircraft equipped with aircraft beacon lights
in accordance with exemplary embodiments of the invention may be
folded up during taxiing without compromising safety. In this way,
the space requirements for taxiing may be reduced, while still
emitting reliable signalling in the form of a comprehensive beacon
light output.
The at least one light source may be at least one LED. In this way,
the light output may be provided in a particularly power-efficient
manner. Also, the maintenance requirements for the aircraft beacon
light may be kept low. The at least one LED may be at least one
colored LED, as will be explained below.
The housing and the lens cover are shaped to embed the aircraft
beacon light into a hinge assembly of an aircraft wing, coupling
the foldable wing tip and the main wing portion. The hinge assembly
may allow for a rotation of the foldable wing tip with respect to
the main wing portion. In particular, the hinge assembly may
comprise a first hinge part, which is attached to or which is an
integral part of the main wing portion, and a second hinge part,
which is attached to or which is an integral part of the foldable
wing tip. For example, the first hinge part may comprise a
plurality of first teeth, and the second hinge part may comprise a
plurality of second teeth. The first and second teeth may be in
engagement along a rotation axis. For example, a rotation rod or
rotation axle may extend through the first and second teeth. The
housing and the lens cover may be shaped to embed the aircraft
beacon light into any suitable portion of the hinge assembly of the
aircraft wing. For example, the housing and the lens cover may be
shaped to embed the aircraft beacon light into one of the plurality
of first teeth.
The housing and the lens cover are shaped to embed the aircraft
beacon light into a hinge assembly of an aircraft wing, coupling
the foldable wing tip and the main wing portion. In other words,
the housing and the lens cover are shaped to be integrated into the
hinge assembly of the aircraft wing. In yet other words, the
aircraft beacon light has a size, weight, and space envelope that
allows for embedding it into the hinge assembly. The space
envelope, as defined by the housing and the lens cover, may fit
into a corresponding recess in the hinge assembly.
The aircraft beacon light is configured to emit flashes of red
light in operation. This wording relates to the perception of the
light output by the observer. For example, a person on the
airfield, when in the output range of the aircraft beacon light,
sees red light flashes emitted by the aircraft beacon light. The
term red light encompasses any kind of reddish shade of light. In a
particular embodiment, the aircraft beacon light may be configured
to emit flashes of aviation red light in operation. The term
aviation red refers to a range of shades of red light, particularly
well-suited to aircraft operations. The color range of aviation red
may for example be as defined in section 25.1397 of the Federal
Aviation Regulations (FAR).
According to a further embodiment, the housing and the lens cover
are shaped to embed the aircraft beacon light into a lateral end of
the main wing portion of the aircraft wing. In this way, the
aircraft beacon light may be very well-positioned for providing an
additional beacon light output in a lateral direction from the
aircraft. In particular, the general orientation of the aircraft
beacon light may correspond well to the shadow cast by the foldable
wing tip, when in a folded up position. A desired beacon light
output, filling the gap created by said shadow, may be achieved
with low complexity, such as a low number of optical elements, and
high efficiency.
According to a further embodiment, the lens cover has a
substantially flat lens cover portion configured to form part of a
side face of the main wing portion of the aircraft wing, when the
foldable wing tip is in a folded up position. In this way, the lens
cover may be well-adapted to forming an engagement face of the main
wing portion in the hinge assembly. Also, said flat lens cover
portion may be covered by the foldable wing tip, when in the
laterally extended position. In this way, an inadvertent emission
of beacon light output may be prevented, when the foldable wing tip
is in the laterally extended position. Also, forming part of the
side face of the main wing portion allows for a good alignment
between the general orientation of the aircraft beacon light and
the shadow cast by the foldable wing tip, when in a folded up
position.
According to a further embodiment, the lens cover has a lens cover
portion configured to form part of an underside of the main wing
portion. In a particular embodiment, the aircraft beacon light may
be configured to emit part of its beacon light output through the
lens cover portion that forms part of the underside of the main
wing portion. In this way, said part of the beacon light output may
be emitted into the aircraft environment, also when the foldable
wing tip is in the laterally extended position.
According to a further embodiment, the at least one light source is
at least one red light source, in particular at least one red LED.
In other words, the light source or light sources inherently emit
light of red color. In this way, the lens cover and the optical
system, if present, can pass on the red light in an unaltered
manner, with flashes of red light being output by the aircraft
beacon light.
According to a further embodiment, the lens cover is or comprises a
red light filter. In other words, the lens cover is or comprises a
filter adapted to filter out all light except for red light. In
this way, light sources emitting a combination of colors, such as
white LEDs or other white light sources, can be conveniently used
for the aircraft beacon light. The lens cover itself may be the red
light filter. It is also possible that the lens cover comprises a
red light filter, which may be arranged on the inside thereof.
Exemplary embodiments of the invention further include an aircraft
wing, comprising a main wing portion; a foldable wing tip; a hinge
assembly coupling the main wing portion and the foldable wing tip;
and an aircraft beacon light, as described in any of the
embodiments above, embedded into the hinge assembly. The additional
features, modifications, and beneficial effects, discussed above
with respect to the aircraft beacon light in accordance with
exemplary embodiments of the invention, apply to the aircraft wing
in an analogous manner.
According to a further embodiment, the hinge assembly is configured
to allow for a motion of the foldable wing tip between a laterally
extended position and a folded up position.
According to a further embodiment, the foldable wing tip exposes at
least part of the lens cover of the aircraft beacon light, when in
the folded up position. The foldable wing tip may block light
emitted through said part of the lens cover, when in the laterally
extended position. The foldable wing tip may expose substantially
all or all of the lens cover of the aircraft beacon light, when in
the folded up position, and may block light emitted through
substantially all or all of the lens cover of the aircraft beacon
light, when in the laterally extended position. In this way, the
aircraft beacon light may have an un-impeded light output path,
when the foldable wing tip is in the folded up position. Also, the
aircraft beacon light may be arranged at a position that is
completely blocked off from the outside environment, when the
foldable wing tip is in the laterally extended position. In this
way, a high degree of freedom for positioning the aircraft beacon
light is provided. A light output path from the aircraft beacon
light during flight operation, i.e. when the foldable wing tip is
in the laterally extended position, is not required.
According to a further embodiment, the hinge assembly comprises a
plurality of first teeth, which are an integral part of the main
wing portion, and a plurality of second teeth, which are an
integral part of the foldable wing tip, and the aircraft beacon
light is arranged in one of the plurality of first teeth. The
plurality of first teeth may be in engagement with the plurality of
second teeth. A rotation axis may run through the plurality of
first teeth and the plurality of second teeth. A rotation axle or
rod may run through the plurality of first teeth and the plurality
of second teeth, enabling their relative rotation, while providing
attachment therebetween.
According to a further embodiment, the aircraft beacon light is
configured to emit the flashes of red light over a horizontal
opening angle of between 5.degree. and 30.degree., in particular
over a horizontal opening angle of between 5.degree. and
20.degree., further in particular over a horizontal opening angle
of between 5.degree. and 15.degree.. In this way, the horizontal
opening angle may be similar to the horizontal blocking angle of
the foldable wing tip. The term horizontal opening angle refers to
the opening angle of the light output in the horizontal
cross-sectional plane through the aircraft beacon light. The term
horizontal may refer to the orientation of the aircraft beacon
light, when installed in the aircraft wing of the aircraft. The
horizontal opening angle may be measured as that angle where the
aircraft beacon light fulfils the illumination requirements as laid
out in Federal Aviation Regulations (FAR) section 25.1401.
According to a further embodiment, the aircraft beacon light is
configured to emit the flashes of red light over a vertical opening
angle of between 5.degree. and 180.degree., in particular over a
vertical opening angle of between 5.degree. and 150.degree.,
further in particular over a vertical opening angle of between
5.degree. and 30.degree.. For the upper end of the broader value
ranges, the vertical opening angle may be such that a full vertical
slice of the illumination requirements, as laid out in Federal
Aviation Regulations (FAR) section 25.1401, may be fulfilled. For
the most narrow value ranges, the vertical opening angle may be
similar to the vertical blocking angle of the foldable wing tip.
The term vertical opening angle refers to the opening angle of the
light output in a vertical cross-sectional plane through the
aircraft beacon light. The term vertical may refer to the
orientation of the aircraft beacon light, when installed in the
aircraft wing of the aircraft. The vertical cross-sectional plane
may run through the center of the horizontal opening angle or may
be any other vertical cross-sectional plane within the horizontal
opening angle, as discussed above. The vertical opening angle may
be measured as that angle where the aircraft beacon light fulfils
the illumination requirements as laid out in Federal Aviation
Regulations (FAR) section 25.1401.
According to a further embodiment, the aircraft beacon light is
configured to emit the flashes of red light over a solid angle
containing a projection of the foldable wing tip, when in the
folded up position. In particular, the projection may be made from
an upper portion of the aircraft fuselage, for which the aircraft
wing is built and/or to which the aircraft wing is attached in
operation. Further in particular, the projection may be made from
the position of an upper fuselage-mounted aircraft beacon light. In
this way, it may be ensured that the aircraft beacon light fills
the entire gap in the beacon light output, created by the shadow of
the foldable wing tip, when in the folded up position.
According to a further embodiment, the aircraft beacon light is
configured to emit the flashes of red light over a solid angle
containing a projection of an engine, arranged on the aircraft
wing. In particular, the projection may be made from a lower
portion of the aircraft fuselage, for which the aircraft wing is
built and/or to which the aircraft wing is attached in operation.
Further in particular, the projection may be made from the position
of a lower fuselage-mounted aircraft beacon light. In this way, it
may be ensured that the aircraft beacon light fills the entire gap
in the beacon light output, created by the shadow of the engine.
According to a further embodiment, the aircraft beacon light may be
configured to emit at least part of the light output that contains
the projection of the engine through a portion of the lens cover on
the underside of the aircraft wing.
Exemplary embodiments of the invention further include an aircraft,
comprising a fuselage, a right aircraft wing, as described in any
of the embodiments above, and a left aircraft wing, as described in
any of the embodiments above. The right aircraft wing and the left
aircraft wing are attached to the fuselage. The aircraft may
further comprise an upper fuselage-mounted beacon light configured
to emit flashes of red light in operation and a lower
fuselage-mounted beacon light configured to emit flashes of red
light in operation. The additional features, modifications, and
beneficial effects, discussed above with respect to the aircraft
beacon light in accordance with exemplary embodiments of the
invention and the aircraft wing in accordance with exemplary
embodiments of the invention, apply to the aircraft in an analogous
manner.
According to a further embodiment, the aircraft is an air
plane.
Exemplary embodiments of the invention further include an aircraft
beacon light system, comprising an upper fuselage-mounted beacon
light configured to emit flashes of red light in operation; a lower
fuselage-mounted beacon light configured to emit flashes of red
light in operation; a right wing aircraft beacon light, as
described in any of the embodiments above; and a left wing aircraft
beacon light, as described in any of the embodiments above. The
additional features, modifications, and beneficial effects,
discussed above with respect to the aircraft beacon light in
accordance with exemplary embodiments of the invention, apply to
the aircraft beacon light system in an analogous manner. In
particular, the right and left aircraft beacon lights may be
well-suited to fill gaps in the beacon light output stemming from
the blocking of light from the upper and lower fuselage-mounted
beacon lights by the right and left foldable wing tips, when in the
folded up position. The right and left aircraft beacon lights may
further be well-suited to fill gaps in the beacon light output
stemming from the blocking of light from the upper and lower
fuselage-mounted beacon lights by the right and left engines,
mounted to the right and left aircraft wings.
According to a further embodiment, the upper fuselage-mounted
beacon light, the lower fuselage-mounted beacon light, the right
wing tip beacon light and the left wing tip beacon light are
synchronized with respect to emitting the flashes of red light. In
particular, the upper fuselage-mounted beacon light, the lower
fuselage-mounted beacon light, the right wing aircraft beacon light
and the left wing aircraft beacon light may be synchronized, such
that the flash frequency is below 180 flashes per minute in overlap
areas between the light outputs of the individual beacon lights.
Synchronization may allow for a reliable signalling of running
engines of the aircraft, while preventing a sensory overload on the
part of the observers of the aircraft.
Exemplary embodiments of the invention further include a method of
supplementing an aircraft beacon light system having an upper
fuselage-mounted beacon light and a lower fuselage-mounted beacon
light, the method comprising emitting flashes of red light from a
hinge assembly of an aircraft wing, the hinge assembly coupling a
foldable wing tip and a main wing portion of the aircraft wing,
when the foldable wing tip of the aircraft wing is in a folded up
position. The additional features, modifications, and beneficial
effects, discussed above with respect to the aircraft beacon light
in accordance with exemplary embodiments of the invention, with
respect to the aircraft wing in accordance with exemplary
embodiments of the invention, with respect to the aircraft in
accordance with exemplary embodiments of the invention, and with
respect to the aircraft beacon light system in accordance with
exemplary embodiments of the invention, apply to the method of
supplementing an aircraft beacon light system in an analogous
manner.
According to a further embodiment, said emitting flashes of red
light comprises emitting flashes of red light over a solid angle
containing a projection of the foldable wing tip, when in the
folded up position, as projected from the position of the upper
fuselage-mounted beacon light.
According to a further embodiment, said emitting flashes of red
light comprises emitting flashes of red light over a solid angle
containing a projection of an engine, arranged on the aircraft
wing, as projected from the position of the lower fuselage-mounted
beacon light.
BRIEF DESCRIPTION OF THE DRAWINGS
Further exemplary embodiments of the invention are described with
respect to the accompanying drawings, wherein:
FIG. 1 shows a schematic top view of an aircraft in accordance with
an exemplary embodiment of the invention, the aircraft being
equipped with two aircraft beacon lights, arranged in the wings of
the aircraft, in accordance with exemplary embodiments of the
invention;
FIG. 2 shows a perspective view of a foldable wing tip and a part
of a main wing portion of an aircraft wing in accordance with an
exemplary embodiment of the invention, the aircraft wing being
equipped with an aircraft beacon light in accordance with an
exemplary embodiment of the invention;
FIG. 3 shows a perspective view of a foldable wing tip and a part
of a main wing portion of an aircraft wing in accordance with an
exemplary embodiment of the invention, the aircraft wing being
equipped with an aircraft beacon light in accordance with another
exemplary embodiment of the invention;
FIG. 4 shows a schematic cross-sectional view through an aircraft
beacon light in accordance with an exemplary embodiment of the
invention;
FIG. 5 illustrates a beacon light output, as emitted by an aircraft
beacon light in accordance with an exemplary embodiment of the
invention, in the context of the schematic top view of the aircraft
of FIG. 1;
FIG. 6 illustrates a beacon light output, as emitted by an aircraft
beacon light in accordance with an exemplary embodiment of the
invention, in the context of a schematic front view of an aircraft
in accordance with an exemplary embodiment of the invention;
FIG. 7 illustrates a beacon light output, as emitted by an aircraft
beacon light in accordance with another exemplary embodiment of the
invention, in the context of the schematic top view of the aircraft
of FIG. 1;
FIG. 8 illustrates a beacon light output, as emitted by an aircraft
beacon light in accordance with another exemplary embodiment of the
invention, in the context of a schematic front view of an aircraft
in accordance with an exemplary embodiment of the invention;
and
FIG. 9 illustrates the change in the beacon light output, as
illustrated in FIG. 8, for the foldable wing tip being in a
laterally extended position.
DETAILED DESCRIPTION
FIG. 1 shows a schematic top view of an aircraft 2, in particular
an air plane 2, comprising a fuselage 4 and two wings 6 extending
laterally from the fuselage 4. An engine 7 is mounted to each of
the wings 6, respectively. The air plane 2 is substantially
symmetric with respect to its longitudinal axis L. Each of the
wings 6 has a main wing portion 62 and a foldable wing tip 64. In
particular, the right wing 6 has a right main wing portion 62 and a
right foldable wing tip 64, and the left wing 6 has a left main
wing portion 62 and a left foldable wing tip 64. Respective
rotation axes between the main wing portions 62 and the foldable
wing tips 64 are indicated with dashed lines in FIG. 1.
The aircraft 2 is provided with an upper fuselage-mounted beacon
light 10 and a lower fuselage-mounted beacon light 12. Both the
upper fuselage-mounted beacon light 10 and the lower
fuselage-mounted beacon light 12 are configured to emit flashes of
red light in operation. The upper fuselage-mounted beacon light 10
has a 360.degree. beacon light output in the horizontal plane and
fulfils the FAR requirements for beacon lights for the upper
hemisphere. The lower fuselage-mounted beacon light 12 has a
360.degree. beacon light output in the horizontal plane and fulfils
the FAR requirements for beacon lights for the lower hemisphere.
The lower fuselage-mounted beacon light 12 is depicted in phantom
in FIG. 1, as it is blocked from view by the fuselage 4 of the
aircraft 2 in the viewing direction of FIG. 1.
The aircraft 2 is further provided with two aircraft beacon lights
8 in accordance with exemplary embodiments of the invention. One of
the aircraft beacon lights 8 is provided in the right wing, while
the other one of the aircraft beacon lights 8 is provided in the
left wing. The aircraft beacon lights 8 are also shown in phantom,
because they are blocked from view by the wing structures of the
right and left wings 6 of the aircraft 2 in the viewing direction
of FIG. 1. The aircraft beacon lights 8 are arranged in the hinge
assemblies, coupling the respective foldable wing tip 64 and the
respective main wing portion 62 of the aircraft wing in question.
Accordingly, the aircraft beacon lights 8 are depicted at the
rotation axes between the main wing portions 62 and the foldable
wing tips 64 in the schematic illustration of FIG. 1. The aircraft
beacon lights 8 are configured to supplement the beacon light
output, as provided by the upper and lower fuselage-mounted beacon
lights 10, 12, when the foldable wing tips 64 are in a folded up
position. The upper and lower fuselage-mounted beacon lights 10, 12
and the aircraft beacon lights 8 in the right and left wings of the
aircraft 2 form an aircraft beacon light system in accordance with
an exemplary embodiment of the invention.
FIG. 2 shows a perspective view of a right foldable wing tip 64 and
a part of a right main wing portion 62 of an aircraft wing 6 in
accordance with an exemplary embodiment of the invention. A hinge
assembly 66 is provided for coupling the main wing portion 62 and
the foldable wing tip 64. The hinge assembly 66 allows for moving
the foldable wing tip 64 between a folded up position and a
laterally extended position with respect to the main wing portion
62. FIG. 2 shows an intermediate position during the transition
from the folded up position of the foldable wing tip 64 to the
laterally extended position of the foldable wing tip 64. By folding
up the foldable wing tip 64 on the ground, the wing span of the
aircraft may be reduced, making the taxiing on an airport easier
and saving parking space at the gate or on the airfield.
In the depicted embodiment of FIG. 2, the hinge assembly 66
comprises a plurality of first teeth 68 on the side of the main
wing portion 62 and a plurality of second teeth 70 on the side of
the foldable wing tip 64. The plurality of first teeth 68 and the
plurality of second teeth 70 mesh. They are in engagement with each
other. In particular, the plurality of first teeth 68 and the
plurality of second teeth 70 are engaged with each other via a
rotation axle or rotation rod or similar structure. The foldable
wing tip 64 is thus rotatable with respect to the main wing portion
62. In the exemplary embodiment of FIG. 2, the plurality of first
teeth 68 are an integral part of the main wing portion 62 and the
plurality of second teeth 70 are an integral part of the foldable
wing tip 64.
The wing 6 is equipped with an aircraft beacon light 8 in
accordance with an exemplary embodiment of the invention. In
particular, the hinge assembly 66 of the wing 6 is provided with
the aircraft beacon light 8. Further in particular, the aircraft
beacon light 8 is arranged in one of the plurality of first teeth
8. In this way, the aircraft beacon light 8 is arranged in the
portion of the hinge assembly 66 that is in the main wing portion
62. The aircraft beacon light 8 is embedded into the hinge assembly
66.
The aircraft beacon light 8 has a housing and a lens cover 84, as
will be described below with respect to FIG. 4. The housing is
integrated into the hinge assembly and is therefore blocked from
view in the viewing direction of FIG. 2. However, lens cover 84 of
the aircraft beacon light 8 is visible in FIG. 2. The lens cover is
arranged in the lateral end of the main wing portion 62. In
particular, the lens cover 84 forms the side face of the one of the
plurality of first teeth 68, into which the aircraft beacon light 8
is embedded. In this way, the lens cover 84 forms part of the side
face of the main wing portion 62. While the lens cover 84 is
covered by the foldable wing tip 64, when the foldable wing tip 64
is in the laterally extended position, the foldable wing tip 64
exposes the lens cover 84, when being moved to the folded up
position. In the exemplary embodiment of FIG. 2, the lens cover 84
is a substantially flat element, forming the substantially flat
side face of said one of the plurality of first teeth 68.
It is pointed out that the wing 6 may have multiple aircraft beacon
lights 8 in accordance with exemplary embodiments of the invention.
For example, two or more aircraft beacon lights may be arranged in
two or more of the plurality of first teeth 68. It is further
pointed out that the hinge assembly may by implemented differently.
The meshing teeth are merely an exemplary embodiment. The aircraft
beacon light in accordance with exemplary embodiments of the
invention may be arranged at any position in the hinge assembly
that allows for light emission to a lateral outside of the
aircraft, when the foldable wing tip 64 is in a folded up
position.
FIG. 3 shows a perspective view of a right foldable wing tip 64 and
a part of a right main wing portion 62 of an aircraft wing 6 in
accordance with an exemplary embodiment of the invention. The wing
6 is very similar to the wing 6 of FIG. 2, with like elements being
denoted with like reference numerals. Reference is made to the
description thereof above. The aircraft beacon light 8 of FIG. 3
differs from the aircraft beacon light 8 of FIG. 2 in that the lens
cover 84 is more extensive. In particular, the lens cover 84 of the
aircraft beacon light 8 of FIG. 3 forms the side face of said one
of the plurality of first teeth 68 and part of an underside of said
one of the plurality of first teeth 68. In this way, the lens cover
84 has a larger area, which may be used for light emission. Also,
part of the light emission may take place through the part of the
lens cover 84 that is on the underside of the main wing portion 62.
This may allow for an easier inspection of the aircraft beacon
light 8.
FIG. 4 shows a schematic cross-sectional view through an aircraft
beacon light 8 in accordance with an exemplary embodiment of the
invention. The aircraft beacon light 8 may be used as the aircraft
beacon light 8 of the aircraft wing 6 of FIG. 3. The schematic
cross-sectional view of FIG. 4 is a vertical cross-sectional view
through the aircraft beacon light 8, when assembled in an
aircraft.
The aircraft beacon light 8 has a housing 82, a lens cover 84, and
a light source 86. In the exemplary embodiment of FIG. 4, the light
source 86 is an LED, which is arranged on a printed circuit board
88. In particular, the light source 86 is a red LED. The aircraft
beacon light 8 is configured to emit flashes of red light in
operation. In particular, the light source 86 may be provided with
electric power in a pulsed manner, in order to emit the flashes of
red light. The aircraft beacon light 8 may have a control unit that
provides pulses of electric current to the light source 86, in
order to generate the flashes of red light. The lens cover 84 may
be a transparent plastics cover. In particular, the lens cover 84
may pass light of all wavelengths therethrough. It is also possible
that the light source 86 emits white light and that the lens cover
84 is a red light filter.
In the exemplary embodiment of FIG. 4, the aircraft beacon light 8
further comprises a collimating lens 90. The collimating lens 90
forms the optical system of the aircraft beacon light 8. It shapes
the light output of the aircraft beacon light 8. It is also
possible that the aircraft beacon light 8 has additional or other
optical elements. In particular, the aircraft beacon light 8 may
have one or more lenses and/or one or more reflectors and/or one or
more shutters. In other words, the optical system of the aircraft
beacon light 8 may be comprised of various optical elements. The
beacon light output of the aircraft beacon light 8 is illustrated
by three exemplary light rays in FIG. 4 and is generally denoted
with reference numeral 50.
FIG. 5 illustrates a beacon light output 50, as emitted by an
aircraft beacon light 8 in accordance with an exemplary embodiment
of the invention, in the context of the schematic top view of the
aircraft 2 of FIG. 1. In FIG. 5, the foldable wing tip 64 of the
right wing 6 of the aircraft 2 is shown in a folded up position.
Being in the folded up position, the foldable wing tip 64 is shown
as a thin structure, corresponding to the thickness of the foldable
wing tip 64. Being in the folded up position, the foldable wing tip
64 exposes the side face of the main wing portion 62, such that the
aircraft beacon light 8 may emit its beacon light output into the
aircraft environment. The beacon light output consists of a
sequence of flashes of red light.
In the schematic top view of FIG. 5, the beacon light output 50 is
illustrated as an illumination cone, leaving the aircraft beacon
light 8 laterally outwards in the aircraft frame of reference. In
other words, the aircraft beacon light 8 emits a beacon light
output 50 laterally outwards. FIG. 5 further depicts a projection
52 of the foldable wing tip 64, when in the folded up position. The
projection 52 is illustrated as a cone, leaving the upper
fuselage-mounted beacon light 10 and enveloping the longitudinal
extension of the foldable wing tip 64 in the aircraft frame of
reference. In the depicted horizontal drawing plane, the projection
52 is a sector having an opening angle of about 10.degree..
The beacon light output 50 is a wider cone than the projection 52
of the foldable wing tip 64. The aircraft beacon light 8 is thus
able to fill the entire gap in the beacon light output of the upper
fuselage-mounted beacon light 10 that is created due to the light
blocking by the folded up foldable wing tip 64. In the depicted
horizontal drawing plane, the beacon light output 50 is a sector
having an opening angle of about 15.degree.. As can be seen from
the angles between the projection 52 and the beacon light output
50, the beacon light output fills the entire gap at some lateral
distance from the foldable wing tip 64. In this way, the beacon
light output of the entire beacon light system is perceived as
undisturbed by the folded up foldable wing tip 64 at some distance
from the foldable wing tip 64.
It is understood that the considerations laid out above with
respect to the right wing 6 apply to the left wing 6 in an
analogous manner. For ease of illustration, the projection 52 and
the beacon light output 50 are depicted for the right wing 6
only.
The upper fuselage-mounted bacon light, the lower fuselage-mounted
beacon light, the aircraft beacon light 8 in the right wing 6, also
referred to as right wing aircraft beacon light, and the aircraft
beacon light 8 in the left wing 6, also referred to as left wing
aircraft beacon light, are synchronized. In other words, the timing
of the flashes of the lights may be adapted to each other. In a
particular embodiment, the lights may be adapted to emit the
flashes of red light at substantially the same points in time and
for substantially the same durations.
FIG. 6 illustrates a beacon light output 50, as emitted by an
aircraft beacon light 8 in accordance with an exemplary embodiment
of the invention, in the context of a schematic front view of an
aircraft 2 in accordance with an exemplary embodiment of the
invention. The aircraft 2 may be the aircraft 2 of FIGS. 1 and 5.
Like elements are denoted with like reference numerals, and
reference is made to the description thereof above. In FIG. 6, only
the left wing 6 is shown. It is understood that the aircraft 2 has
a substantially mirror-symmetric right wing.
In the schematic front view of FIG. 6, the beacon light output 50
is illustrated as an illumination cone, leaving the aircraft beacon
light 8 laterally outwards in the aircraft frame of reference, i.e.
to the right in the drawing plane of FIG. 6. As is apparent from
looking at FIGS. 5 and 6, the beacon light output 50 is a
three-dimensional illumination cone, having both a horizontal
opening angle and a vertical opening angle. FIG. 6 further depicts
the projection 52 of the foldable wing tip 64, when in the folded
up position, as seen from the front of the aircraft 2. The
projection 52 is illustrated as a cone, leaving the upper
fuselage-mounted beacon light 10. The lower line of the projection
52 corresponds to the lowest light emission direction of the upper
fuselage-mounted beacon light 10. The upper line of the projection
runs along the upper end of the foldable wing tip 64. The
projection 52 corresponds to the shadow created by the folded up
foldable wing tip 64. In the depicted vertical drawing plane, the
projection 52 is a sector having an opening angle of between
5.degree. and 10.degree..
The beacon light output 50 is a wider cone than the projection 52
of the foldable wing tip 64. The aircraft beacon light 8 is thus
able to fill the entire gap in the beacon light output of the upper
fuselage-mounted beacon light 10 that is created due to the light
blocking by the folded up foldable wing tip 64. In the depicted
vertical drawing plane, the beacon light output 50 is a sector
having an opening angle of about 20.degree.. As can be seen from
the angles between the projection 52 and the beacon light output
50, the beacon light output fills the entire gap at some lateral
distance from the foldable wing tip 64. In this way, the beacon
light output of the entire beacon light system is perceived as
undisturbed by the folded up foldable wing tip 64 at some distance
from the foldable wing tip 64.
FIG. 7 illustrates a beacon light output 54, as emitted by an
aircraft beacon light 8 in accordance with another exemplary
embodiment of the invention, in the context of the schematic top
view of the aircraft 2 of FIG. 1. In FIG. 7, the foldable wing tip
64 of the right wing 6 of the aircraft 2 is shown in a folded up
position. Being in the folded up position, the foldable wing tip 64
is shown as a thin structure, corresponding to the thickness of the
foldable wing tip 64. The illustration of FIG. 7 is thus similar to
the illustration of FIG. 5. Being in the folded up position, the
foldable wing tip 64 exposes the side face of the main wing portion
62.
In the exemplary embodiment of FIG. 7, the aircraft beacon light 8
has a lens cover that is partly arranged on the side face of the
main wing portion 62 and partly arranged on the underside of the
main wing portion 62. The aircraft beacon light 8 of FIG. 7 may be
the aircraft beacon light 8, as described with respect to FIGS. 3
and 4. This will be described in more detail with respect to FIGS.
8 and 9 below. The aircraft beacon light 8 of FIG. 7 is configured
to emit part of its beacon light output via the part of the lens
cover on the side face of the main wing portion 62 and part of its
beacon light output via the part of the lens cover on the underside
of the main wing portion 62. The beacon light output consists of a
sequence of flashes of red light.
In the schematic top view of FIG. 7, the beacon light output 54 is
illustrated as an illumination cone, leaving the aircraft beacon
light 8 laterally outwards in the aircraft frame of reference. In
other words, the aircraft beacon light 8 emits a beacon light
output 54 laterally outwards. FIG. 7 further depicts a projection
56 of the engine 7. The projection 56 is illustrated as a cone,
leaving the lower fuselage-mounted beacon light 12 and enveloping
the longitudinal extension of the engine 7 in the aircraft frame of
reference. In the depicted horizontal drawing plane, the projection
56 is a sector having an opening angle of about 30.degree..
The beacon light output 54 is a wider cone than the projection 56
of the engine 7. The aircraft beacon light 8 is thus able to fill
the entire gap in the beacon light output of the lower
fuselage-mounted beacon light 12 that is created due to the light
blocking by the engine 7. In the depicted horizontal drawing plane,
the beacon light output 54 is a sector having an opening angle of
about 45.degree.. As can be seen from the angles between the
projection 56 and the beacon light output 54, the beacon light
output fills the entire gap at some lateral distance from the
foldable wing tip 64. In this way, the beacon light output of the
entire beacon light system is perceived as undisturbed by the
folded up foldable wing tip 64 at some distance from the aircraft
2.
It is understood that the considerations laid out above with
respect to the right wing 6 apply to the left wing 6 in an
analogous manner. For ease of illustration, the projection 56 and
the beacon light output 54 are depicted for the right wing 6
only.
FIG. 8 illustrates a beacon light output 54, as emitted by an
aircraft beacon light 8 in accordance with another exemplary
embodiment of the invention, in the context of a schematic front
view of an aircraft 2 in accordance with an exemplary embodiment of
the invention. The aircraft 2 may be the aircraft 2 of FIGS. 1 and
7. Like elements are denoted with like reference numerals, and
reference is made to the description thereof above. In FIG. 8, only
the left wing 6 is shown. It is understood that the aircraft 2 has
a substantially mirror-symmetric right wing.
In the schematic front view of FIG. 8, the beacon light output 54
is illustrated as an illumination cone, leaving the aircraft beacon
light 8 laterally outwards in the aircraft frame of reference, i.e.
to the right in the drawing plane of FIG. 8. As is apparent from
looking at FIGS. 7 and 8, the beacon light output 54 is a
three-dimensional illumination cone, having both a horizontal
opening angle and a vertical opening angle. FIG. 8 further depicts
the projection 56 of the engine 7, as seen from the front of the
aircraft 2. The projection 56 is illustrated as a cone, leaving the
lower fuselage-mounted beacon light 12. The upper line of the
projection 56 corresponds to the highest light emission direction
of the lower fuselage-mounted beacon light 12. The lower line of
the projection 56 runs along the lower end of the engine 7. The
projection 56 corresponds to the shadow created by the engine 7. In
the depicted vertical drawing plane, the projection 56 is a sector
having an opening angle of about 10.degree..
The beacon light output 54 is a wider cone than the projection 56
of the engine 7. The aircraft beacon light 8 is thus able to fill
the entire gap in the beacon light output of the lower
fuselage-mounted beacon light 12 that is created due to the light
blocking by the engine 7. In the depicted vertical drawing plane,
the beacon light output 54 is a sector having an opening angle of
about 20.degree.. As can be seen from the angles between the
projection 56 and the beacon light output 54, the beacon light
output fills the entire gap at some lateral distance from the
aircraft 2. In this way, the beacon light output of the entire
beacon light system is perceived as undisturbed by the engine 7 at
some distance from the aircraft 2.
FIG. 9 illustrates the change in the beacon light output 54, as
illustrated in FIG. 8, for the foldable wing tip 64 being in a
laterally extended position. The modified beacon light output is
referred to as beacon light output 54'. As stated above, the
aircraft beacon light 8 of FIGS. 7 to 9 emits part of its beacon
light output 54 through the part of the lens cover on the side face
of the main wing portion 62 and part of its beacon light output 54
through the part of the lens cover on the underside of the main
wing portion 62. When the foldable wing tip 64 is in the laterally
extended position, as illustrated in FIG. 9, it blocks that part of
the beacon light output 54 that is emitted through the part of the
lens cover on the side face of the main wing portion 62. Some or
all of the part of the beacon light output 54 that is emitted
through the part of the lens cover on the underside of the main
wing portion 62 is still emitted into the aircraft environment.
This is illustrated via the modified beacon light output 54' in
FIG. 9. In this way, the gap in the beacon light output of the
lower fuselage-mounted beacon light 12, created due to the light
blocking by the engine 7, may be partly or entirely filled by the
modified beacon light output 54', although the foldable wing tip 64
blocks part of the beacon light output 54.
An aircraft beacon light according to exemplary embodiments of the
invention may have a beacon light output 50, as illustrated with
respect to FIGS. 5 and 6, or may have a beacon light output 54, as
illustrated with respect to FIGS. 7 to 9. It is also possible that
an aircraft beacon light has both the beacon light output 50, as
illustrated with respect to FIGS. 5 and 6, and the beacon light
output 54, as illustrated with respect to FIGS. 7 to 9. In the
latter case, the aircraft beacon light may have dedicated light
sources and optical systems for the beacon light output 50 on the
one hand and for the beacon light output 54 on the other hand. For
example, the aircraft beacon light may have at least one first
light source and a first optical system for generating the beacon
light output 50 and may have at least one second light source and a
second optical system for generating the beacon light output 54. It
is also possible that the aircraft beacon light has an extended
beacon light output that fills both the gaps in the beacon light
outputs from the fuselage-mounted beacon lights due to the engine
and the folded up foldable wing tip. The horizontal opening angle
of such an extended beacon light output could be about 90.degree.
for filling both gaps. It is also possible that separate aircraft
beacon lights, each targeted to one of the shadow of the foldable
wing tip 64 and the shadow of the engine 7, are provided in the
hinge assembly of the aircraft wing 6.
While the invention has been described with reference to exemplary
embodiments, it will be understood by those skilled in the art that
various changes may be made and equivalents may be substituted for
elements thereof without departing from the scope of the invention.
In addition, many modifications may be made to adapt a particular
situation or material to the teachings of the invention without
departing from the essential scope thereof. Therefore, it is
intended that the invention not be limited to the particular
embodiment disclosed, but that the invention will include all
embodiments falling within the scope of the appended claims.
* * * * *